Aircraft fuel tank isolator

ABSTRACT

An isolator for an aircraft fuel tank configured to separate an electrically conductive internal panel of the fuel tank from an electrically conductive pipe that passes through the panel. The isolator includes: a plurality of first attachment points for attaching the isolator to the panel, a plurality of second attachment points for attaching the isolator to the pipe, and an aperture defined by an outer wall and extending from a first side of the isolator to a second side of the isolator. The aperture is configured to receive the pipe in use, wherein the isolator is formed of a non-electrically conductive material.

RELATED APPLICATIONS

This application is a continuation of U.S. patent application Ser. No.16/366,128, filed Mar. 27, 2019, which claims priority to United Kingdompatent application GB 1805237.3 filed Mar. 29, 2018, the entirety ofeach of these applications is incorporated by reference.

TECHNICAL FIELD

The present invention relates to an isolator for an aircraft fuel tank,an isolating system, a method and an aircraft.

BACKGROUND

In some aircraft, the aircraft fuel tanks have an irregular shape. Thefuel tanks therefore typically comprise a plurality of segments definedby segment walls, or panels. The panels may extend substantiallyvertically between the top of the wing and the bottom of the wing. Forexample, in some aircraft the fuel tanks are located in the aircraftwings and are positioned around other equipment located in the wing.

Some other equipment, for example located in the wing, may be connectedto the fuselage of the aircraft via pipes that pass through the aircraftfuel tank. In some instances, the pipes pass through the panels of thefuel tank. For example, the pipes may carry hydraulic fluid from ahydraulic supply to a hydraulic actuator. In some instances, the pipesmust pass through the segment walls.

SUMMARY

A first aspect of the present invention provides an isolator for anaircraft fuel tank, the isolator configured to separate an electricallyconductive internal panel of the fuel tank from an electricallyconductive pipe that passes through the panel, the isolator comprising:a plurality of first attachment points for attaching the isolator to thepanel, a plurality of second attachment points for attaching theisolator to the pipe, and an aperture defined by an outer wall andextending from a first side of the isolator to a second side of theisolator, the aperture configured to receive the pipe in use, whereinthe isolator comprises a non-electrically conductive material.

Optionally, the outer wall of the aperture extends outwardly from thefirst side of the isolator to form a tube, wherein the tube isconfigured to pass through the panel in use.

Optionally, the plurality of first attachment points and the pluralityof second attachment points are positioned on a flange extending fromthe outer wall of the aperture.

Optionally, the first attachment points comprise a counterbore extendingfrom the second side of the isolator to the first side of the isolator,wherein the wider end of the counterbore extends from the second side ofthe isolator.

Optionally, the first attachment points are positioned around theaperture to align with corresponding panel apertures in the panel.

Optionally, the second attachment points comprise a counterboreextending from the first side of the isolator to the second side of theisolator, wherein the wider end of the counterbore extends from thefirst side of the isolator.

Optionally, the second attachment points are positioned around theaperture to align with corresponding fitting apertures in a pipe fittingfixed to the pipe.

Optionally, the isolator comprises a groove on the first side and/or thesecond side of the isolator, the groove extending around the outer wallof the aperture and configured to receive a seal.

Optionally, the isolator is formed from a chemically inert material.

A second aspect of the present invention provides an isolation systemcomprising: an isolator according to the first aspect of the presentinvention, a plurality of first bolts, wherein each bolt of theplurality of first bolts is positioned in the counterbore of arespective one of the plurality of first attachments of the isolator,and a plurality of second bolts, wherein each bolt of the plurality ofsecond bolts is positioned in the counterbore of a respective one of theplurality of second attachments of the isolator.

Optionally, wherein at least one of the plurality of first and secondbolts are electrically-conductive, the system comprising anon-electrically conductive sealant covering the head of the at leastone of the plurality of first and second bolts to seal the head of eachbolt in its respective counterbore.

Optionally, the isolation system comprises a seal in a groove of theisolator, the seal surrounding the outer wall of the aperture.

A third aspect of the present invention provides a method of isolatingan electrically conductive internal panel or an aircraft fuel tank froman electrically conductive pipe that passes through the panel, themethod comprising: passing the pipe through a tube of a non-electricallyconductive material isolator, passing the tube through an aperture inthe panel, rigidly attaching the isolator to a pipe fitting fixed to thepipe, and rigidly attaching the isolator to the panel.

Optionally, the method comprises: rigidly attaching the isolator to apipe fitting fixed to the pipe with an electrically-conductive firstfastener, electrically insulating the first fastener from the panel,rigidly attaching the isolator to the panel with anelectrically-conductive second fastener, and electrically insulating thesecond fastener from the pipe.

Optionally, the method comprises providing a seal between the isolatorand the panel. Optionally, the seal is a liquid gasket.

A fourth aspect of the present invention provides as aircraftcomprising: as isolator according to the first aspect of the presentinvention, or an isolation system according to the second aspect of thepresent invention.

BRIEF DESCRIPTION OF THE DRAWINGS

Embodiments of the invention will now be described, by way of exampleonly, with reference to the accompanying drawings, in which:

FIG. 1 shows a schematic isometric view of an isolator according toembodiments of the present invention;

FIG. 2 shows a schematic cross-sectional view of an isolation systemaccording to embodiments of the present invention, the isolating systemcomprising the isolator of FIG. 1;

FIG. 3 is a flow diagram showing a method according to embodiments ofthe present invention; and

FIG. 4 shows a schematic top view of an aircraft according toembodiments of the present invention.

DETAILED DESCRIPTION

There can be a build-up of static electricity in an aircraft fuel tank,and/or the aircraft may be struck by lightning. In some aircraft, thepanels and the pipes comprise or are formed from an electricallyconductive material and may therefore carry an electrical current.Accordingly, it can be beneficial to isolate a panel from a pipe toprevent an electrical current from passing between the panel and pipe.

FIG. 1 shows an isometric view of an isolator 100 according toembodiments of the present invention. The isolator 100 is for anaircraft fuel tank and is configured to separate an electricallyconductive internal panel of the fuel tank from an electricallyconductive pipe that passes through the panel.

The isolator 100 comprises a plurality of first attachment points 110for attaching the isolator 100 to the panel, a plurality of secondattachment points 120 for attaching the isolator 100 to the pipe, and anaperture 130 defined by an outer wall 140 and extending from a firstside 102 of the isolator 100 to a second side 104 of the isolator 100.The aperture 130 is configured to receive the pipe in use.

In some embodiments, the outer wall 140 of the aperture 130 extendsoutwardly from the first side 102 of the isolator 100 to form a tube.The tube is configured to pass through the panel in use. In someembodiments, the outer wall 140 extends from the first side 102 of theisolator 100 by a distance that is greater than a thickness of thepanel. The length of the tube is greater than a thickness of theisolator 100. That is, the length of the tube is greater than thedistance between the first side 102 of the isolator 100 and the secondside 104 of the isolator 100.

In some embodiments, the plurality of first attachment points 110 andthe plurality of second attachment points 120 are positioned on a flange106 extending from the outer wall 140 of the aperture 130. The flange106 may define the first side 102 and the second side 104 of theisolator 100. The flange 106 of the isolator 100 shown in FIG. 1 ischamfered around the first and second attachment points 110, 120. Thiscan help to reduce the size and therefore weight of the isolator 120.

In some embodiments, the first attachment points 110 are configured toreceive a fastener (not shown) for fastening the isolator to the paneland/or the second attachment points 120 may be configured to receive afastener (not shown) for fastening the isolator to the pipe.

In some embodiments, the first attachment points 110 are positionedaround the aperture 130 to align with corresponding panel apertures inthe panel (not shown). In some embodiments, the second attachment points120 are positioned around the aperture 130 to align with correspondingfitting apertures in a pipe fitting fixed to the pipe (not shown). Theisolator 100 shown in FIG. 1 has three first attachment points 110 eachat a first radial distance from the aperture 130 and three secondattachment points 120 each at a second radial distance from the aperture130. In some embodiments, the first and the second radial distance arethe same.

In some embodiments, the isolator comprises two or more first attachmentpoints 110. In some embodiments, the isolator comprises two or moresecond attachment points 120. The isolator 100 shown in FIG. 1 has firstattachment points 110 alternately spaced between the second attachmentpoints 120 so that the attachment points 110, 120 are equally spacedaround the aperture 130. This configuration can help to evenlydistribute the load through the isolator 100 in use, thus helping toreduce the stresses on the isolator 100 in use.

In some embodiments, the first attachment points 110 are oriented in anopposite direction to the second attachment points 120. Each of thefirst attachment points 110 of the isolator 100 shown in FIG. 1comprises a first counterbore extending from a wider end of the firstcounterbore at the second side 104 of the isolator 100 to a thinner endof the first counterbore at the first side 102 of the isolator 100. Eachof the second attachment points 120 of the isolator 100 shown in FIG. 1comprise a second counterbore extending from a wider end of the secondcounterbore at the first side 102 of the isolator 100 to a thinner endof the second counterbore at the second side 104 of the isolator 100.The wider end 122 of the counterbore extends from the first side 102 ofthe isolator 100. In some embodiments, the thinner end of the firstand/or second counterbores is threaded and configured to receive acorresponding threaded bolt.

In other embodiments, the first attachment points 110 and/or the secondattachment points 120 may be any other shape suitable for attaching theisolator 100 to the panel and the pipe, respectively.

The isolator 100 shown in FIG. 1 comprises a first groove 150 on thefirst side 102 of the isolator 100. The first groove 150 extends aroundthe outer wall 140 of the aperture 130 and is configured to receive afirst seal (not shown). In other embodiments, the first groove 150 maybe omitted. In some embodiments, the isolator 100 comprises a secondgroove 160 (as shown in FIG. 2) on the second side 104 of the isolator100. The second groove 160 extends around the aperture 130 and isconfigured to receive a second seal. In other embodiments, the secondgroove 160 may be omitted. In use, the first and second seals may helpto prevent fuel from passing from one side of the panel to another andmay help to further isolate the panel from the pipe.

The isolator 100 comprises a non-electrically conductive material. Insome embodiments, the non-electrically conductive material does notreact to aircraft fuel or hydraulic fluid. Such a material helps toprevent premature degradation of the isolator 100 in use, and may helpto prevent contamination of the fuel due to degradation of the isolator100. In some embodiments, the isolator 100 comprises another materialthat is coated by the non-electrically conductive material. In otherembodiments, the isolator 100 is formed from only the non-electricallyconductive material, for example the isolator 100 is machined from ablock of the non-electrically conductive material or the isolator 100 ismoulded from the non-electrically conductive material. In someembodiments, the isolator 100 comprises a single part. In otherembodiments, the isolator 100 is formed from two or more parts rigidlyfixed together, for example by a mechanical fastening or by chemicalmeans such as an adhesive. In some embodiments, the isolator 100 isformed from a chemically inert material, for example nylon.

FIG. 2 shows a schematic cross-sectional view of an isolation system 10according to embodiments of the present invention. The isolation system10 comprises an isolator 100 according to embodiments of the presentinvention, for example the isolator 100 shown in FIG. 1. The isolationsystem 10 further comprises a plurality of first bolts 12 and aplurality of second bolts 16. Each bolt of the plurality of first bolts12 is positioned in the counterbore of a respective one of the pluralityof first attachments 110 of the isolator 100. Each bolt of the pluralityof second bolts 16 is positioned in the counterbore of a respective oneof the plurality of second attachments 120 of the isolator 100. Each ofthe plurality of plurality of first bolts 12 is held in position by arespective first nut 14. Each of the plurality of second bolts 16 isheld in position by a respective second nut 18.

FIG. 2 shows the isolation system 10 in use. That is, the isolator 100is positioned in an aircraft fuel tank. The isolator 100 is fastened toa pipe fitting 6, through which a pipe 4 passes, by the plurality ofsecond bolts 16. In this embodiment, the pipe fitting 6 and the pipe 4are electrically conductive. The outer wall 140 of the isolator 100extends through an isolator aperture 3 of a panel 1. The panel 1 extendsthrough the aircraft fuel tank. The isolator 100 is fastened to thepanel 1 by the plurality of first bolts 12. In some embodiments, thepanel 1 is an internal wall of the fuel tank and a different isolator isused at an intersection between the pipe 4 and an external wall of thefuel tank.

As can be seen in FIG. 2, the outer wall 140 of the isolator 100 ispositioned between the panel 1 and the pipe fitting 6 in use. In someembodiments, such as embodiments in which the pipe fitting 6 iselectrically conductive, the outer wall 140 is configured to extend fromthe first side 102 of the isolator 100 by a distance that exceeds thewidth of the panel 1 and by an additional distance that prevents anelectrical arc (see dashed line 50 in FIG. 2, for example) formingbetween the panel 1 and the pipe fitting 6 or the pipe 4. In someembodiments, the flange 106 of the isolator 100 has a thickness that issufficient to help prevent an electrical arc (see dashed line 60 in FIG.2, for example) forming between the pipe panel 1 and the pipe fitting 6.

The first attachment points 110 are positioned on the flange 106 of theisolator 100 to align with corresponding panel apertures 2 in the panel1. The second attachment points 120 are positioned on the flange 106 ofthe isolator 100 to align with corresponding fitting apertures 7 in thepipe fitting 6. In some embodiments, the isolator 100 is configured suchthat the first attachments points 110 are at a radial distance from theouter wall 140 that is sufficient to help prevent an electrical arcforming between the plurality of first bolts 12 and the pipe fitting 6or the pipe 4 (see dashed line 70 in FIG. 2, for example).

When the plurality of first and second bolts 12, 16 are positioned intheir respective counterbores, respective voids 13, 17 are formed aroundthe head of each bolt. In some embodiments, at least one of theplurality of first and second bolts 12, 16 are electrically-conductive.In such embodiments, the system 10 comprises a non-electricallyconductive sealant (not shown) covering the head of the at least one ofthe plurality of first and second bolts 12, 16 to seal the head of eachbolt in its respective counterbore. In some embodiments, the sealantfills the void 13, 17. In some embodiments, the sealant is formed from achemically inert material. In use, the sealant helps to prevent anelectrical arc (see dashed line 70 in FIG. 2, for example) formingbetween the first bolts 12 and the pipe 4 and/or the pipe fitting 6 andbetween the second bolts 16 and the panel 1.

The isolation system 10 shown in FIG. 2 comprises an isolator 100comprising a first groove 150 on the first side 102 of the isolator 100and around the outer wall 140. The isolation system 10 comprises a firstseal 29 located in the first groove 150 of the isolator 100. The firstseal 29 surrounds the outer wall 140 of the isolator 100. By way ofexample only, the first seal 29 is an O-ring. In use, as shown in FIG.2, the first seal 29 is positioned between the isolator 100 and thepanel 1. The first seal 29 further helps to isolate the panel 1 from thepipe 4. The first seal 29 may also help to prevent leakage of fuelthrough the panel aperture 3.

In some embodiments, the isolation system 10 comprises an isolator 100that does not comprise the first groove 150. In such embodiments, aliquid sealant or liquid gasket (not shown) may be provided between thepanel 1 and the first side 102 of the isolator 100. The liquid sealantfurther helps to isolate the panel 1 from the pipe 4.

The isolation system 10 shown in FIG. 2 comprises an isolator 100comprising a second groove 160 on the second side 104 of the isolator100 and around the aperture 130. The isolation system 10 comprises asecond seal 30 located in the second groove 160 of the isolator 100. Thesecond seal 30 surrounds the aperture 130 on the second side 104 of theisolator 100. By way of example only, the second seal 30 is an O-ring.In use, as shown in FIG. 2, the second seal 30 is positioned between theisolator 100 and pipe fitting 4. The second seal 30 further helps toisolate the panel 1 from the pipe 4. The second seal 30 may also help toprevent leakage of fuel through the panel aperture 3.

In some embodiments, the isolation system 10 comprises an isolator 100that does not comprise the second groove 160. In such embodiments, aliquid sealant or liquid gasket (not shown) may be provided between thepipe fitting 4 and the second side 104 of the isolator 100. The liquidsealant further helps to isolate the panel 1 from the pipe 4.

FIG. 3 shows a flow diagram of a method 300 of isolating an electricallyconductive internal panel or an aircraft fuel tank from an electricallyconductive pipe that passes through the panel, according to embodimentsof the present invention. The method 300 comprises: passing 310 the pipethrough a tube of a non-electrically conductive material isolator,passing 320 the tube through an aperture in the panel, rigidly attaching330 the isolator to a pipe fitting fixed to the pipe, and rigidlyattaching 340 the isolator to the panel.

In some embodiments, the isolator is an isolator 100 according toembodiments of the present invention.

In some embodiments, the rigidly attaching 330 comprises removablyrigidly attaching the isolator to the pipe fitting fixed to the pipe. Insome embodiments, the rigidly attaching 340 comprises removably rigidlyattaching the isolator to the panel. For example, the isolator may beattached to the pipe fitting and the panel by fasteners.

In some embodiments, the rigidly attaching 330 comprises rigidlyattaching the isolator to the pipe fitting with anelectrically-conductive first fastener and the method compriseselectrically insulating 350 the first fastener from the panel. In someembodiments, the rigidly attaching 340 comprises rigidly attaching theisolator to the panel with an electrically-conductive second fastenerand the method comprises electrically insulating 360 the second fastenerfrom the pipe. In some embodiments, the electrical insulating 350, 360may be achieved by providing a non-electrically conductive sealant overthe first and second fasteners.

In some embodiments, the method comprises providing 370 a seal betweenthe isolator and the panel. In some embodiments, the seal may beprovided in a groove of the isolator, for example the first and/orsecond grooves 150, 160 of the isolator 100 shown in FIG. 2. In otherembodiments, the seal may be a liquid gasket between a surface of thepanel and an adjacent surface of the isolator and/or between a surfaceof the pipe fitting and the isolator.

FIG. 4 shows a schematic top view of an aircraft 400 according toembodiments of the present invention. The aircraft 400 comprises afuselage 410 and wings 420. In some embodiments, the wings 420 areformed from a non-electrically conductive material, for example carboncomposite. In some embodiments, the wings 420 are formed from anon-electrically conductive material, for example carbon composite. Inother aircraft, wings are formed from an electrically-conductivematerial and may not require an isolator according to the presentinvention because the wings themselves may dissipate an electricalcurrent.

In some embodiments, an aircraft fuel tank is located in the wings 420.In some embodiments, the aircraft 400 comprises one or more isolators100 according to the present invention. In some embodiments, the one ormore isolators 100 are located in the aircraft fuel tank, the one ormore isolators 1000 being fixed one or more respective internal panels 1of the aircraft fuel tank. In some embodiments, the aircraft 400comprises one or more isolation systems 10 according to embodiments ofthe present invention. The one or more isolation systems 10 being fixedto one or more respective internal panels 1 of the aircraft fuel tank.

It is to noted that the term “or” as used herein is to be interpreted tomean “and/or”, unless expressly stated otherwise.

The above embodiments are to be understood as non-limiting illustrativeexamples of how the present invention, and aspects of the presentinvention, may be implemented. Further examples of the present inventionare envisaged. It is to be understood that any feature described inrelation to any one embodiment may be used alone, or in combination withother features described, and may also be used in combination with oneor more features of any other of the embodiments, or any combination ofany other of the embodiments. Furthermore, equivalents and modificationsnot described above may also be employed without departing from thescope of the present invention, which is defined in the accompanyingclaims.

1. An isolator for an aircraft fuel tank, the isolator configured toseparate an electrically conductive internal panel of the fuel tank froman electrically conductive pipe that passes through the panel, theisolator comprising: a plurality of first attachment points configuredto attach the isolator to the panel, a plurality of second attachmentpoints configured to attach the isolator to the pipe, and an aperturedefined by an outer wall and extending from a first side of the isolatorto a second side of the isolator, the aperture configured to receive thepipe, wherein the isolator comprises a non-electrically conductivematerial, and wherein each of the plurality of first attachment pointsis configured to receive a fastener for fastening the isolator to thepanel and each of the plurality of second attachment points isconfigured to receive a fastener for fastening the isolator to the pipe.2. The isolator according to claim 1, wherein the plurality of firstattachment points are oriented in an opposite direction to the pluralityof second attachment points.
 3. The isolator according to claim 1,wherein the plurality of first attachment points and the plurality ofsecond attachment points are positioned on a flange extending from theouter wall of the aperture.
 4. The isolator according to claim 3,wherein the flange is chamfered around the first and second attachmentpoints.
 5. The isolator according to claim 1, wherein each of the firstattachment points are positioned at substantially the same radialdistance from the aperture.
 6. The isolator according to claim 1,wherein each of the second attachment points are positioned atsubstantially the same radial distance from the aperture.
 7. Theisolator according to claim 1, wherein each of the first and secondattachment points are positioned at substantially the same radialdistance from the aperture.
 8. The isolator according to claim 1,wherein the first and second attachment points are alternately spacedaround the aperture.
 9. The isolator according to claim 1, wherein thefirst and second attachment points are equally spaced around theaperture.
 10. The isolator according to claim 1, wherein the isolator isformed from only the non-electrically conducting material.
 11. Anisolation system comprising: the isolator according to claim 1, aplurality of first bolts each received by a respective first attachmentpoint, and a plurality of second bolts each received by a respectivesecond attachment point.
 12. The isolation system according to claim 11,wherein at least one of the plurality of first and second bolts areelectrically-conductive, the isolation system comprising anon-electrically conductive sealant covering the head of the at leastone of the plurality of first and second bolts.
 13. A method ofisolating an electrically conductive internal panel of an aircraft fueltank from an electrically conductive pipe that passes through the panel,the method comprising: passing the pipe through a tube of anon-electrically conductive material isolator, passing the tube throughan aperture in the panel, rigidly attaching the isolator to a pipefitting fixed to the pipe with a first fastener, the first fastenerreceived by a first attachment point of the isolator, and rigidlyattaching the isolator to the panel with a second fastener, the secondfastener received by a second attachment point of the isolator.
 14. Themethod according to claim 13, wherein the first and second fasteners areelectrically conductive, and wherein the method comprises: electricallyinsulating the first fastener from the panel, and electricallyinsulating the second fastener from the pipe.
 15. An aircraft comprisingthe isolator according to claim
 1. 16. An aircraft according to claim15, further comprising wings formed from a non-electrically conductivematerial.
 17. An apparatus comprising: the isolator according to claim1, and an electrically conductive pipe.